EP2457825B1 - Flugzeughydraulikantriebssystem - Google Patents

Flugzeughydraulikantriebssystem Download PDF

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Publication number
EP2457825B1
EP2457825B1 EP11191062.6A EP11191062A EP2457825B1 EP 2457825 B1 EP2457825 B1 EP 2457825B1 EP 11191062 A EP11191062 A EP 11191062A EP 2457825 B1 EP2457825 B1 EP 2457825B1
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EP
European Patent Office
Prior art keywords
actuator
aircraft
aircraft central
power source
central hydraulic
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Active
Application number
EP11191062.6A
Other languages
English (en)
French (fr)
Other versions
EP2457825A3 (de
EP2457825A2 (de
Inventor
Atsushi Fukui
Norimasa Takagi
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Nabtesco Corp
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Nabtesco Corp
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Filing date
Publication date
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Publication of EP2457825A2 publication Critical patent/EP2457825A2/de
Publication of EP2457825A3 publication Critical patent/EP2457825A3/de
Application granted granted Critical
Publication of EP2457825B1 publication Critical patent/EP2457825B1/de
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Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C13/00—Control systems or transmitting systems for actuating flying-control surfaces, lift-increasing flaps, air brakes, or spoilers
    • B64C13/24—Transmitting means
    • B64C13/38—Transmitting means with power amplification
    • B64C13/40—Transmitting means with power amplification using fluid pressure
    • B64C13/42—Transmitting means with power amplification using fluid pressure having duplication or stand-by provisions
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F15—FLUID-PRESSURE ACTUATORS; HYDRAULICS OR PNEUMATICS IN GENERAL
    • F15B—SYSTEMS ACTING BY MEANS OF FLUIDS IN GENERAL; FLUID-PRESSURE ACTUATORS, e.g. SERVOMOTORS; DETAILS OF FLUID-PRESSURE SYSTEMS, NOT OTHERWISE PROVIDED FOR
    • F15B2211/00—Circuits for servomotor systems
    • F15B2211/20—Fluid pressure source, e.g. accumulator or variable axial piston pump
    • F15B2211/205—Systems with pumps
    • F15B2211/20576—Systems with pumps with multiple pumps
    • F15B2211/20592—Combinations of pumps for supplying high and low pressure
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F15—FLUID-PRESSURE ACTUATORS; HYDRAULICS OR PNEUMATICS IN GENERAL
    • F15B—SYSTEMS ACTING BY MEANS OF FLUIDS IN GENERAL; FLUID-PRESSURE ACTUATORS, e.g. SERVOMOTORS; DETAILS OF FLUID-PRESSURE SYSTEMS, NOT OTHERWISE PROVIDED FOR
    • F15B2211/00—Circuits for servomotor systems
    • F15B2211/30—Directional control
    • F15B2211/305—Directional control characterised by the type of valves
    • F15B2211/30505—Non-return valves, i.e. check valves
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F15—FLUID-PRESSURE ACTUATORS; HYDRAULICS OR PNEUMATICS IN GENERAL
    • F15B—SYSTEMS ACTING BY MEANS OF FLUIDS IN GENERAL; FLUID-PRESSURE ACTUATORS, e.g. SERVOMOTORS; DETAILS OF FLUID-PRESSURE SYSTEMS, NOT OTHERWISE PROVIDED FOR
    • F15B2211/00—Circuits for servomotor systems
    • F15B2211/50—Pressure control
    • F15B2211/505—Pressure control characterised by the type of pressure control means
    • F15B2211/50509—Pressure control characterised by the type of pressure control means the pressure control means controlling a pressure upstream of the pressure control means
    • F15B2211/50536—Pressure control characterised by the type of pressure control means the pressure control means controlling a pressure upstream of the pressure control means using unloading valves controlling the supply pressure by diverting fluid to the return line
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F15—FLUID-PRESSURE ACTUATORS; HYDRAULICS OR PNEUMATICS IN GENERAL
    • F15B—SYSTEMS ACTING BY MEANS OF FLUIDS IN GENERAL; FLUID-PRESSURE ACTUATORS, e.g. SERVOMOTORS; DETAILS OF FLUID-PRESSURE SYSTEMS, NOT OTHERWISE PROVIDED FOR
    • F15B2211/00—Circuits for servomotor systems
    • F15B2211/50—Pressure control
    • F15B2211/575—Pilot pressure control
    • F15B2211/5753—Pilot pressure control for closing a valve
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F15—FLUID-PRESSURE ACTUATORS; HYDRAULICS OR PNEUMATICS IN GENERAL
    • F15B—SYSTEMS ACTING BY MEANS OF FLUIDS IN GENERAL; FLUID-PRESSURE ACTUATORS, e.g. SERVOMOTORS; DETAILS OF FLUID-PRESSURE SYSTEMS, NOT OTHERWISE PROVIDED FOR
    • F15B2211/00—Circuits for servomotor systems
    • F15B2211/60—Circuit components or control therefor
    • F15B2211/63—Electronic controllers
    • F15B2211/6303—Electronic controllers using input signals
    • F15B2211/6306—Electronic controllers using input signals representing a pressure
    • F15B2211/6313—Electronic controllers using input signals representing a pressure the pressure being a load pressure
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F15—FLUID-PRESSURE ACTUATORS; HYDRAULICS OR PNEUMATICS IN GENERAL
    • F15B—SYSTEMS ACTING BY MEANS OF FLUIDS IN GENERAL; FLUID-PRESSURE ACTUATORS, e.g. SERVOMOTORS; DETAILS OF FLUID-PRESSURE SYSTEMS, NOT OTHERWISE PROVIDED FOR
    • F15B2211/00—Circuits for servomotor systems
    • F15B2211/60—Circuit components or control therefor
    • F15B2211/63—Electronic controllers
    • F15B2211/6303—Electronic controllers using input signals
    • F15B2211/6336—Electronic controllers using input signals representing a state of the output member, e.g. position, speed or acceleration
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F15—FLUID-PRESSURE ACTUATORS; HYDRAULICS OR PNEUMATICS IN GENERAL
    • F15B—SYSTEMS ACTING BY MEANS OF FLUIDS IN GENERAL; FLUID-PRESSURE ACTUATORS, e.g. SERVOMOTORS; DETAILS OF FLUID-PRESSURE SYSTEMS, NOT OTHERWISE PROVIDED FOR
    • F15B2211/00—Circuits for servomotor systems
    • F15B2211/60—Circuit components or control therefor
    • F15B2211/665—Methods of control using electronic components
    • F15B2211/6651—Control of the prime mover, e.g. control of the output torque or rotational speed
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F15—FLUID-PRESSURE ACTUATORS; HYDRAULICS OR PNEUMATICS IN GENERAL
    • F15B—SYSTEMS ACTING BY MEANS OF FLUIDS IN GENERAL; FLUID-PRESSURE ACTUATORS, e.g. SERVOMOTORS; DETAILS OF FLUID-PRESSURE SYSTEMS, NOT OTHERWISE PROVIDED FOR
    • F15B2211/00—Circuits for servomotor systems
    • F15B2211/70—Output members, e.g. hydraulic motors or cylinders or control therefor
    • F15B2211/71—Multiple output members, e.g. multiple hydraulic motors or cylinders
    • F15B2211/7107—Multiple output members, e.g. multiple hydraulic motors or cylinders the output members being mechanically linked
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F15—FLUID-PRESSURE ACTUATORS; HYDRAULICS OR PNEUMATICS IN GENERAL
    • F15B—SYSTEMS ACTING BY MEANS OF FLUIDS IN GENERAL; FLUID-PRESSURE ACTUATORS, e.g. SERVOMOTORS; DETAILS OF FLUID-PRESSURE SYSTEMS, NOT OTHERWISE PROVIDED FOR
    • F15B2211/00—Circuits for servomotor systems
    • F15B2211/80—Other types of control related to particular problems or conditions
    • F15B2211/875—Control measures for coping with failures
    • F15B2211/8757—Control measures for coping with failures using redundant components or assemblies

Definitions

  • the flight controller 12 constitutes a controller of this embodiment that controls the backup hydraulic pump 18 such that the backup hydraulic pump 18 is operated at the occurrence of a loss or degradation in the function of at least one of the first aircraft central hydraulic power source 104 and the second aircraft central hydraulic power source 105.
  • the equalization processing unit 26 adjusts command signals to the first actuator 14a and the second actuator 14b according to the sign and the size of the value of difference between the differential pressure signals.
  • the state of connection of the control valve 17a is switched in accordance with a command signal from the actuator controller 11a and the state of connection of the control valve 17b is switched in accordance with a command signal from the actuator controller 11b. Consequently, the first and second actuators (14a, 14b) are operated in synchronization, and thereby the aileron 103a is driven with a high drive moment.
  • the present invention can be widely applied as an aircraft actuator hydraulic system that includes hydraulically operated actuators for driving a control surface of an aircraft and that supplies pressure oil to the actuators.
  • the present invention is not limited to the above-described embodiment, and all modifications, applications and equivalents thereof that fall within the claims, for which modifications and applications would become apparent by reading and understanding the present specification, are intended to be embraced therein.

Landscapes

  • Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Automation & Control Theory (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Fluid-Pressure Circuits (AREA)

Claims (2)

  1. Flugzeugaktuator-Hydrauliksystem (1), das hydraulisch betätigte Aktuatoren (14a, 14b) zum Antreiben einer Steuerfläche (103a) eines Flugzeugs (100) umfasst und das Drucköl zu den Aktuatoren (14a, 14b) führt, wobei das System (1) Folgendes umfasst:
    einen ersten Aktuator (14a), der als einer der Aktuatoren bereitgestellt ist und der die Steuerfläche (103a) antreibt, indem er durch die Beschickung mit Drucköl von einer ersten zentralen Flugzeughydraulikkraftquelle (104), die eine erste zentrale Flugzeughydraulikpumpe (104a) umfasst, betätigt wird;
    einen zweiten Aktuator (14b), der als ein anderer der Aktuatoren bereitgestellt ist und der die Steuerfläche (103a) antreibt, indem er durch die Beschickung mit Drucköl von einer zweiten zentralen Flugzeughydraulikkraftquelle (105), die eine zweite zentrale Flugzeughydraulikpumpe (105a) umfasst, betätigt wird; und
    eine Reservehydraulikpumpe (18), die im Inneren eines Tragflügels (102a) des Flugzeugs (100) installiert ist und die den ersten Aktuator (14a) mit Drucköl beschicken kann, wenn es zu einem Verlust oder einer Minderung einer Funktion der ersten zentralen Flugzeughydraulikkraftquelle (104) und/oder der zweiten zentralen Flugzeughydraulikkraftquelle (105) kommt,
    gekennzeichnet durch die Tatsache, dass ein maximaler Förderdruck der Reservehydraulikpumpe (18) auf einen größeren Wert einzustellen ist als maximale Förderdrücke der ersten zentralen Flugzeughydraulikpumpe (104a) und der zweiten zentralen Flugzeughydraulikpumpe (105a).
  2. Flugzeugaktuator-Hydrauliksystem (1) nach Anspruch 1,
    das des Weiteren eine Steuereinheit (12) umfasst, welche die Reservehydraulikpumpe (18) so steuert, dass die Reservehydraulikpumpe (18) betätigt wird, wenn ein Verlust oder eine Minderung einer Funktion der ersten zentralen Flugzeughydraulikkraftquelle (104) und/oder der zweiten zentralen Flugzeughydraulikkraftquelle (105) eintritt,
    wobei die Steuereinheit (12) während eines normalen Betriebes, wo es weder zu einem Verlust noch zu einer Minderung einer Funktion der ersten zentralen Flugzeughydraulikkraftquelle (104) oder die zweiten zentralen Flugzeughydraulikkraftquelle (105) gekommen ist, die Reservehydraulikpumpe (18) so steuert, dass die Reservehydraulikpumpe (18) ebenfalls betätigt wird, falls eine Bedingung einer hohen Antriebsleistung erfüllt ist, wobei die Bedingung darin besteht, dass ein Moment, der zum Antreiben der Steuerfläche (103a) erforderlich ist, größer ist als zuvor festgelegte Antriebsmomente, die durch den ersten Aktuator (14a), der mit dem Drucköl von der ersten zentralen Flugzeughydraulikkraftquelle (104) betätigt wird, und den zweiten Aktuator (14b), der mit dem Drucköl von der zweiten zentralen Flugzeughydraulikkraftquelle (105) betätigt wird, erzeugt werden können.
EP11191062.6A 2010-11-29 2011-11-29 Flugzeughydraulikantriebssystem Active EP2457825B1 (de)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US41770610P 2010-11-29 2010-11-29

Publications (3)

Publication Number Publication Date
EP2457825A2 EP2457825A2 (de) 2012-05-30
EP2457825A3 EP2457825A3 (de) 2017-05-10
EP2457825B1 true EP2457825B1 (de) 2018-04-11

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ID=45047641

Family Applications (1)

Application Number Title Priority Date Filing Date
EP11191062.6A Active EP2457825B1 (de) 2010-11-29 2011-11-29 Flugzeughydraulikantriebssystem

Country Status (3)

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US (1) US8505848B2 (de)
EP (1) EP2457825B1 (de)
JP (1) JP5658117B2 (de)

Families Citing this family (16)

* Cited by examiner, † Cited by third party
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JP5514621B2 (ja) * 2010-04-28 2014-06-04 ナブテスコ株式会社 航空機アクチュエータの油圧装置
JP5603651B2 (ja) * 2010-05-13 2014-10-08 ナブテスコ株式会社 航空機アクチュエータの油圧装置
JP5503431B2 (ja) * 2010-06-30 2014-05-28 ナブテスコ株式会社 航空機アクチュエータの油圧システム
JP5666233B2 (ja) * 2010-10-08 2015-02-12 ナブテスコ株式会社 航空機アクチュエータの油圧装置
JP5658117B2 (ja) * 2010-11-29 2015-01-21 ナブテスコ株式会社 航空機アクチュエータの油圧システム
JP2013147049A (ja) * 2012-01-17 2013-08-01 Nabtesco Corp 航空機アクチュエータの油圧システム
JP5905294B2 (ja) * 2012-02-27 2016-04-20 ナブテスコ株式会社 航空機アクチュエータの油圧システム
JP6178571B2 (ja) 2012-12-26 2017-08-09 三菱航空機株式会社 動翼のアクチュエータ装置、航空機の動翼、及び、航空機
JP6178587B2 (ja) * 2013-02-28 2017-08-09 三菱航空機株式会社 航空機のアクチュエータ装置、及び、航空機
EP3219608B1 (de) * 2016-03-18 2020-07-08 Ratier-Figeac SAS Verbesserte hydraulische betätigungssteuerung in propellern
WO2017187934A1 (ja) * 2016-04-27 2017-11-02 Smc株式会社 シリンダの動作状態監視装置
JP6868166B2 (ja) * 2016-10-03 2021-05-12 Smc株式会社 シリンダの動作状態監視装置
JP6944627B2 (ja) 2016-10-03 2021-10-06 Smc株式会社 シリンダの動作状態監視装置
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Also Published As

Publication number Publication date
JP5658117B2 (ja) 2015-01-21
EP2457825A3 (de) 2017-05-10
US20120131912A1 (en) 2012-05-31
EP2457825A2 (de) 2012-05-30
US8505848B2 (en) 2013-08-13
JP2012116466A (ja) 2012-06-21

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